Lateral control arrangement



Sept 10, 1946.A F. H. cLAusERy Erm.

LATERAL CONTROL ARRANGEMENT Filed sem-8,

1941 7 'sheets-sheet 1 AeLof 6T i700@ mm1/Tom' A TTORNEY Sept. 10, 1946. F. H.- cLAusER ETAL LATERAL CONTROL ARRANGEMENT Filed sept. 8. 1941 7` sheets-sheet 2v FuNc/.s Hmz/5m Mp C Aews 6. Waan a f mvmons ATTORNEY Sept. 10,1946. F. H. cLAusER ETAL A LATERAL CONTROL ARBANGEMENT iled Sept. 8, 1941 7 Sheetsf-Sheei 3 l INVENTORS fefwr/s 64A us5@ Ama BY (421.05 C l/l/ 0D Sept. 10, 1946. n

FQH. cLAusER. Erm.

LATERAL CONTROL ARRANGEMENT Filed Sept. 8, 1941 BY 14,2405 C.

7 Sheets-Sheet 4..

INVENT FMA/as HIM/$52 A aan ATMRNEY Sept. 10, 1946.` f F. H. cLAUsER ETAL LATERAL coN-TRoL ARRANGEMENT 4 Filed Sept. 8, 194 1 7 Sheets-Sheet 5 PAM/sf? fm1/f5@ Ma Sept; 10, A1946. v

l F. H. cLAusER Erm.

LATERAL CONTROL ARRANGEMENT Filed sept. 8, 1941 '7 sheets-sheet e www ATTORNEY Sept. 10, 1946, F. H. cLAusl-:RA ETAL- v 2,407,401

LATERAL CONTROL ARRANGEMENT Filed sept. 8. 1941 l v sxpeets-sheet 'L .FRA/vas b. M0552 wa Amas C Waan lNvEmons I B%u/M l y v ATTORNEY Patented Sept. 10, l1946 2,407,401 LATERAL CONTROL ARRANGEMENT Francis H. Clauser, da

Wood, West Los An Douglas Aircraft Company,

Calif.

rita Monica, and Carlos C.

geles,

Calif., assignors to Inc., Santa Monica,

Application September 8, 1941, Serial No. 410,098

22 Claims. l

Our invention relates to the lateral control oi aircraft and particularly to the control oi high speed aircraft of the type necessitating full span With the ever increasing maximum speed of modern airplanes higher wing loadings the stalling speeds and landing speeds have necessarily increased accordingly. This is undesirable ior the reason that increase landing speeds increasesdanger, particularly in View of the :fact that runway lengths of landing fields generally have not been increased proportionately with the increased landing speeds. l

Some time ago iiaps, or air brakes as they are sometimes called, were added to aircraft along the trailing edge portions of the wings not occupied by ailerons in order to selectively change the lift and drag characteristics of the wings, lower the stalling speed and increase the gliding angle which the aircraft could approach the landing field. This was satisfactory for a time but as aircraft speeds continually increased it became necessary to increase the nap area and it was inieasible to do this by further extension along the trailing edge for the reason that the ailerons, provided `for lateral control, necessarily tool; up a certain portion oi the wing span at the trailing edge.

To overcome this problem, experiments were made with lift spoilers which of the ailerons and adapted to lie 'flush with the top surface of the wing under normal flight conditions. The ailerons were then arranged.A to move downward in the manner of a flap to cooperate With the conventional flaps in increasing the lift and drag of the wing. As the airplane approached the lanong held or slowed down toward stalling speed the conventional ailerons were lowered to increase the wing liit and lateral control of the crait was taken over by the spoilers, these members being raised, one at a time, from their respective flush positions in the wing.

This development was definitely a step in the right direction. However, it soon became apparent that under certa-in ilight conditions spoilers have numerous disadvantages. For one thing, they tend to cause a control lag at the most critical time, that is; at low speeds when positive and immediate control is most needed. Furthermore, spoilers cause a yaw in the craft at a time when it is not desired, such as when the pilot is merely leveling up the airplane withont turning. The discontinuity between a spoiler when raised andthe aileron when the latter is being used as a flap causes a separation of the airilow over the aileron, thus creating undesirwere placed aheadv able drag and lessening desirable lift. The above disadvantages are heightened by the necessity of having the spoiler move upward from its flush position through a relatively large angle in order l to obtain suiiicient lateral control in a full span ilap condition where the aileron at the trailing edge is immovable in level flight.

The fact that spoilers move only upward tends to prevent their use for raising a' wing. In other words, when a pilot wants to level his airplane he may do so only by dropping the high wing. This is particularly serious at landing when it may be necessary to raise the low wing to avoid contact with the ground. Tests have conclusively chown that the full lifting power of a ap cannot be obtained without controlling the flow oi air thereover and, as above stated, such control cannot be obtained from an ordinary spoiler because in order for the spoiler to be truly eiective it is necessary that it rise a considerable amount from its normal flush position in the wing, and in its raised position it necessarily disturbs the flow over the nap.

In addition to the above enumerated spoiler disadvantages as aiecting flight characteristics of an airplane, the spoilers have certain undesirable characteristics from the pilots standpoint. For one thing, they have a tendency to give unsatisfactory stick forces for the reason that when the pilot begins to move one spoiler, the lift created thereon causes'it to rise abruptly and pull the pilots control stick over sharply, Furthermore, there is a tendency to either over-control or under-control the airplane when ying with spoilers, since there is no load ieel which is proportionate to the amount of control as in ordinary ailerons.

Under the present invention an arrangement has been worked out whereby the advantages oi full span naps are obtained with the least sacriice of normal control characteristics and with none of the disadvantages of spoilers.

Accordingly, it is the principal object of our invention to provide a full span ilap arrangement for aircraft which gives satisfactory lateral control characteristics under all ight conditions.

Another object of the invention is to provide a full span flap arrangement by which an airplane may be levelled without introducing undesirable adverse yaw.

Another object of our invention is to provide a full span flap arrangement in which there is no appreciable control lag.

Another object is to provide a full span flap arrangement in which full lateral control can be obtained with only a relatively small movement of the lateral control member.

Another object is to provide a full span flap arrangement in which the flow of air over the ap is controlled to obtain maximum lift increases.

Another object is to provide a full' span ap arrangement in which there are satisfactory lateral control stick forces,

Another object is to provide a full span flap arrangement with low hinge moment characteristics.

Another object is to provide a full span flap arrangement furnishing substantially normal load feel to the pilot under all flight conditions.

Another object is to provide a full span iap arrangement in which the gap between the wing and the flap opens and closes in accordance with the desired control movements and eeots.

Another object is to provide a full span ilap mechanism which selectively varies the movements of the control airfoils in accordance with flight conditions.

Another object is to provide a full span flap mechanism which is compact and of relatively light weight, and which provides suitable and adequate lateral control.

Other and further objects will become apparent after reading the specication and studying the drawings in which:

Figure 1 is a perspective view of an airplane wing with a conventional split trailing edge flap at the inboard end thereof andthe control airfoil arrangement of our invention at the outboard end thereof;

Figure 2 is a fragmentary perspective view of the wing and control airfoils of Figure l, with portions thereof cut away to show one embodiment of a control mechanism for moving the control airfoils;

Figure 3 is a diagrammatic side elevational view of the trailing portion of the airplane wing with control airfoils mounted thereon in neutral high speed or cruising speed position, with broken lines indicating the approximate extent of their diierential rotation about their mounting pivots from their respective neutral positions;

Figure 4 is a fragmentary perspective View of the airplane wing and control airfoils shown in Figure 1, with portions cut away to show the mechanism of Figure 2 and with one of the control airfoils moved to a lift increasing ltakeoi or approach position;

Figure. 5 is a diagrammatic side elevational view of the trailing portion of the airplane wing of Figure 3, with the control airfoils moved to a moderately low speed, takeoff or approach position as indicated in Figure 4, and including broken lines indicating the approximate extent of diierential rotation of the control airfoils from their respective new neutral position;

Figure 6 is a fragmentary perspective view of the airplane wing and control airfoils shown in Figure 1, with portions cut away to show the mechanism, and with one of the control airfoils moved to a maximum lift or landing position;

Figure '7 is a diagrammatic side elevational View oi the trailing portion of the airplane wing of Figure 5, with the control airfoils moved to a maximum lift or landing position as indicated in Figure 6, and including broken lines indicating the approximate extent of rotation of the control airfoils from their respective new neutral position;

Figure 8 is a fragmentary perspective view of the airplane wing and control airfoils mounted thereon, with portions thereof out away to show another embodiment of a control mechanism;

Figure 9 is a fragmentary perspective View of the airplane wing and control airfoils of Figure 8, showing the mechanism displaced whereby one of the airfoils is moved to a lift increasing, takeoff or approach position; and

Figure 10 is a fragmentary perspective View of the airplane wing and control airfoils of Figure 9, showing the mechanism still further displaced whereby one of the airfoils is moved to a maximum lift or landing position.

With reference to the drawings, and particularly Figure 1, an airplane wing l@ is shown as being attached to a fuselage indicated in part by the lines H. The wing carries a conventional ap i3 of the split trailing edge type on the inboard portion and a control airfoil arrangement on the outboard portion. For clarity, both` the conventional flap and the control airfoils of the present invention are shown in a lift increasing position with respect to the wing i5.

Figure 2 is a close-up view of the control airfoil arrangement and is cut away to show a mechanism assembly l2 for controlling the airfoils.

This assembly l2 is pivoted at lll and i5 to a beam I7 forming a part of the wing structure and serves two purposes, namely; to support a pair of control airfoils and to move these control airfoils with respect to the main supporting airfoil to effect lateral control of the airplane to which they are attached. The mechanism assembly l2 includes a carrier member i3 which is connected to the main airfoil structure at the pivot Ill. This carrier member has a pair of laterally protruding arms 2@ and 22 between which is journaled a crank 24. The crank in turn has a pair ofsimilarly protruding arms 26 and 2S. rThe arm 25 is connected by a link Sil at 3l to one of the control members 32. This member 32 functions as an ordinary aileron under all normal flight conditions but, in addition, it may be moved rearward and downward from the position shown in Figure 2 in the manner of a ap under flight conditions requiring increased lift on the main supporting airfoil It. Because of the dual functioning of the member 32 We have termed the member an ailerlap and it will be so referred to hereinafter.

The ailerflap is indirectly carried by the main sup-porting airfoil for pivotal movement with respect thereto through the mechanism assembly l2. It is directly connected to the mechanism assembly at two points; rst, at the pivot 3l previously mentioned and second, at a pivot 34 through a bracket 35, fixed to the ailerap structure. A link 38 extends from the pivot 3d forward to a pivotal connection 5 at the lower extremity of the carrier member i8. A short distance forward of the pivot Sli a link l2 is pivoted to the link 3B at 39 and extends upward to connect with the main airfoil structure beam Il at the pivot i6.

The upper arm 28 of the crank 2li is provided with two adjacent pivotal connections G4 and 46 at its outer extremity. From the pivot 1M a short link 8 extends to a pivotal connection 59 with the center arm of a conventional three-armed bell crank 52 which is in turn pivoted to the main airfoil structure at 53. The other two arms of this bell crank provide attachment for cables 54 and 56 which extend to the pilots compartment and connect to a control member therein Iing edge portion of As may be readily seen in the drawing, when the ailerap is full down it is still controlled by the cables 54, 56 for simultaneous movement with the slot lip about their respective neutral posi'- tions. It may be mentioned here that self-aligning bearings are used in all pivots where there is any displacement ci one member relative to another out of the normal plane of pivot. These bearings ordinarily permit at least a 10 variation on either side oi the pivot plane.

Relative movements of the slot lip and ailerap as eiected through the mechanism assembly while in the latter position are sho-wn in Figure '7, and broken lines |25, |28 and H0, ||2 indicate the upward and downward ranges or" movement of the two members from their respective neutrals. It may be seen that in this maximum lift position of the ailerflap as in all of its positions, the slot lip continues to function in controllingthe Iiow of air over the ailerilap in accordance with the desired lateral control eieet.

In Figures 8, 9, and l we have shown another embodiment of a mechanism for accomplishing the movements of the ailerap and the slot lip as previously described.

Figure 8 shows this mechanism as it appears when the ailerfiap is in its full up or normal position wherein it functions exclusively as an aileron.

Figure 9 shows the mechanism as it appears when the ailerap has been moved to a takeoff or approach position to slightly increase the liit of the main supporting airfoil and at the same time perform ,aileron functions.

Figure 1o shows the mechanism as it appears when the ailerfiap is -in the full down or maximum lift increasing position, wherein it still functions as an aileron but to a lesser extent.

With particular reference now to Figure 8 it may be seen that the basic operating principle of this arrangement is quite similar to that shown in Figures 2, 4, and 6. The mechanism assembly H includes a carrier member I l pivoted to the main airfoil structure at it which pivot, incidentally, is coaxial with the slot lip pivot. The member is in the form of a crank having a central pivot |22 and this same pivot serves as a central turning point for a similar crank |22. Also attached at this pivot is a piston |24 of a hydraulic cylinder |26 identical to the cylinder 92 described inthe previous embodiment. rhis cylinder is likewise pivoted at its closed end to the main airfoil structure.

At the upper end of crank |22 a pivotal connection |28 is provided for a control link |30 corresponding in function to the link 48 in Figure 1. In other words, this link extends to a bell crank to which control cables are attached for movement of the ailerflap and slot lip in either direction from their respective neutral positions. From the pivot |28 a short link |32 extends downwardly and is pivotally connected at |34 to a link |36. The latter link is pivoted at |38 to a bracket Mt fixed to the main airfoil structure. Substantially intermediate the ends of link |36, at the bend therein, there is a pivotal connection |42 for a link IM extending upwardly and connecting at Mii to the slot lip. It is this latter link which transmits the movement of the control link |30 to the slot lip. Movement of the ailerilap is effected by a link |48, pivotally connecting at |50 to the lower end of crank |22 and at |52 to a bracket |54 xed on the upper leadthe ailerlap. The ailerap is supported from the main airfoil structure by a beam |56 similar to the beam in Figure 2 to which is pivoted a link |58 at |50. The link |58 extends downwardly and connects at |6| with an arm |62 which is in turn pivoted at G4 to the lower end of the carrier member H6 and at |66 to a bracket Hi8 fixed to the lower surface of the ailerflap.

Considering the operation of the slot lip and ailerap to move them from their neutral positions, as shown in Figure 8, it may be seen that fore and aft movement of the control link |3il will cause rotation of the crank |22 about its pivot |28. This will transmit movement to the link Hi8 and cause the ailerlap to pivot about point |66. At the same time `the slot lip will be caused to move in ,accordance with the ailerflap by reason of its connection with control link |30 through links |32, |36, and Mii. With the mechanism in this position the relative movements of the two control airfoils as eiected by movement of the control link |3 will be substantially as shown in Figure 2.

In Figure 9 the piston |24 of hydraulic cylinder |26 has been partially extended to move the pivot |29 and likewise the two crank links ||6 and I 22 to the rear about their upper pivots. This act, through the linkage |58 and |62, displaces the ailerflap to a rearward, takeoff or approach position. From this new position simultaneous movement of the two control airfoils is still eiected by fore and aft motion of the control link |3i| but in a changed degree by reason of the change of position of the various links relative to each other. Relative movements of the slot lip and ailerflap are substantially as shown in Figure 5.

In Figure 10 the piston |24 of hydraulic cylinderY |26 has been completely extended, moving the ailerflap still farther aft and downward to a maximum lift position. In this new linkage position rotation of the ailerilap and slot lip about their pivots is effected as before by fore and aft movement of the control link |39 in a still different amount, substantially as shown in f Figure 7.

With both linkage embodiments it may be seen that while the lift of the main airfoil is varied in accordance with night conditions through movement of the ailerflap pivot, both the aileriiap and slot lip retain lateral control eiTectiveness at all times. As the ailerflap moves downward its effect for lateral control gradually decreases but at the same time the movements and effectiveness of the slot lip gradually increase and thus retain ample lateral control with respect to the main airfoil. Satisfactory hinge moments are retained and a substantially constant load feel eiect is provided by the combined movements of the ailerap and slot lip.

While we have herein shown and described our invention in its present and preferred linkage embodiments it will be obvious to those skilled in the art, after understanding the invention, that other mechanisms may be devised to obtain the same relative movements of the two control members both with respect to each other and with respect to the main airfoil. Accordingly, we do not wish to be limited other than by the appended claims.

We claim:

1. In a lateral control device for aircraft, a main supporting airioil, a control member spaced from the trailing edge of said main supporting airfoil to form a slot therebetween, said member being disposed spanwise of said main airfoil for pivotal movement about an axis, a second control member normallyrelatioV with'said main' supporting airi'oil and said `first named control'member and'adapted to pivot about an substantially parallel to the pivotal axis of said first named control member, unitary means operable by the pilot and independently connected :to each of said control members for imparting simultaneous movement to said control members about their respective axes, and means associated with said first named means for changing the position of the axis of said rst named control member with respect to the main supporting airfoil and with respect to its spacing from the axis of said second control member, said unitary means being adapted to re tain control of both of said control members at all the spacing of said control member axes as determined by said first control member axis changing means.

2. In a lateral control device forv aircraft, a main supporting airfoil, a control member spaced from the trailing edge of said main supporting airfoil to form a slot therebetweemsaid member bein-g'disposed spanwise of said main airfoil for pivotal movement about an axis, a second control member normally closing the slot between said main supporting airfoil and said rst named control member, and adapted to pivot aboutan axis substantially parallel to the pivotal axis of said first named control member, and unitary means operable by the pilot and independently connected to each of said 'control members for imparting simultaneous codirectional rotative movement thereto about their respective pivotal axes.

3. In a lateral control device for aircraft, a main supporting airfoil, a'control'mernber spaced from the trailingedge of said main supporting airfoil' to form a'slot therebetween', said member being disposed spanwise of said main airfoil for pivotal movement about an axis, a second control memberriormally disposed in slot closing relationV with said main supporting airfoil and said rst named control member and adapted to pivot about an axis substantially parallel to the pivotal axis ofsaid first named control member, unitary means operable by the pilot andindependently connected to each of said control members for imparting to said control members simultaneous upward Vand simultaneous downward rotative movements about their 'respective pivotal axes from a neutral position, and means associated with saidflrst named means for changing the `rposition of 'the axis of said first named control member with respect to the main supporting airfoil and with respect to its spacing from the axis of said second control member, said unitary means being adapted to retain control of both said control members at all the spacings of said control member axes as determined by Said first control member exis Changing meanse. 1n a lateral Control device for aircraft, a main supporting airfoil, a control member spaced from the treiln-gtedee ,of Said main Supporting airfoil to ferm" .a Slot therebetween, Said member beine disposed Spariwse f saidmain arfoil for pivotal movement about an axis, 4a ksecond control member normally @195mg ib@ S101J between said mail? supporting ,eirfpil andsaid first ,named control member and adapted to pivot about an axis'substaritially wpara lel to the pivotal Aaxis of Said firstname@ @11h01 member, .and unitary I'cnean'sd operable by thewpilot Vand independently @essere 'ie each' efiseid wird ,members iov:

disposdfin slot closing Y 10 imparting thereto simultaneous upward and simultaneousdownward movements about their resp'e'ciilv'e'pvotal -aX's' 'fromn a neutral position.

-'i5/Ina' lateral Acontroldevice for aircraft, a main supporting airfoil, a control member spaced froml the'trailing'ed'g'e of said'main supporting airfoilto forma slottherebetween, said member being disposed spa'nvviseo'fsaid main airfoil for pivotal movementaboutan axis', a'se'cond control member Yric'irrnally disposed in slot closing yrelationwithsaid main supporting airfoil and said first named control member and adapted'to pivot abc'ut'an axis substantially yparallel to the pivotal axis'y of said first'darnedcontrol member, unitary means operable bythe pilot and independently connected Atoeacl'i of'said control members for imparti toY said control members simultaneous upw'* rd and simiiltaneous downward movements about their respect've pivotal axes Afrom a neutral position, mea s for moving the Ypivotal axis cf said iirst control member from a high speed position to one o r various medianpositio-ns and from such median positions toga landing position, said last mentioned means serving to change the rota tive movements of saidncontrol members about their pivotal axes with respect to each other as effected by said unitary controlmeans.v a

6. In a lateral control device for aircraft, a mail? Supporting @Q a @93u01 member pad from the trailing ede@ of ,Said main Surrrtns airf. il t9 iam e Slot thefebtveri Seid member being disposed spanwise of said main airfoil for pivotal'movement about an axis, a second contrel member @mehr 'disposed in Slet Closing ration with seid mais Supporting airfol arid said first named control member and adapted to pivot about an axis substantially parallel'to'the pivotal axis of said rst named control member,

means to displace thc'piv'otal Aaxis of said first name control member rearwardlyand downwardly to lform a slot between said first and second nameddcontrolmembe'r's, and a unitary means to'sfimultaneously' rotate both said control members aboutV their pivotal axes in either direc'- tion of rotation, to increase or decrease the lift of said main sirpporting" air'foil respectively, said anA being so organized and arranged asv to correspondingly decreaserv andv increase respectively thev 'sizeof the'"slot`between said control membvels,

' '7. In a lateral control device for aircraft, a main supporting airfoilfa c'ontrol'inember spaced from the trailing edge of said main'supporting airfoil to form a slot therebetween, said member being disposed spanwise'of said 'main airfoil forpivotal moveinertabout'an' axis, la; second' control member normally" disposed in slot closing relation with' saidmain' 'supporting airfoil and said first named control member "and adapted to pivot about an axis substantially parallell to the pivotal axis ofjsaid'flrsjt 'named' control member, unitary means operable by the'pilotand connected to said controlfmembers for simultaneously and codirectioallyrotating them nbither direction about their respective pivots to increase vor decrease respectively the lift of said main' 'supporting Yairfoil,- lsaid means `being organized and arranged tomove said second control member away from said first control member in slot increasing relation'whensaid members swing upward on their nivo* axes and to move said second control member ward said first control member in vslot decreasing relation when said members swing downward on their lpivotal axes. 4

if 1.1.1 a lateral ,Weird devis@ I9; aircraft a main supporting airfoil, a rst control 'member spaced from the trailing edge of said main supporting airfoil to form a slot therebetween, said member being disposed spanwise of said main airfoil for pivotal movement about an axis, a second control member normally disposed in slot closing relation with said main supporting airfoil and said first named control member and adapted to pivot about an axis substantially parallel to the pivotal axis or" said first control member, a primary member pivoted about an axis, means operatively connecting both said iirst and second control members to said primary pivotal member each of said connections being independent of the other, iirst pilot operated means for rotating said primary pivotal member about its axis to impart simultaneous movement to said first and second control members about their respective pivotal axes, and second pilot operated means for simultaneously changing the positions of said primary pivotal members axis and said iirst control members axis with respect to said main supporting airfoil and with respect to said second control members pivotal axis, said rst pilot operated means being 3;.

adapted to retain control of both said rst and second control members at all the relative positions of said control member axes.

9. In a lateral control device for aircraft, a main supporting airfoil, a'rst control member spaced from the trailing edge of said main supporting airfoil to form a slot therebetween, said member being disposed spanwise of said main airfoil for pivotal movement about an axis, a second control member normally disposedin slot" closing relation with said main Supporting vairioil and said rst control member, and adapted to pivot about an axis substantially parallel to the pivotal axis of said first control member, a primary member pivoted about an axis, means operatively connecting said primary pivotal member to each of said rst and second control members for imparting simultaneous rotative movement thereto in at least two directions from a neutral position each of said connections being independent of the other, c first pilot operated means for rotating said primary pivotal member about its pivotal axisand second pilot operated means for changing the relative neutral positions of said control surfaces and varying the relative movements thereof from said neutral positions as eiected by said first pilot operated means.

10. In a lateral control device for aircraft, a first airfoil, a second airfoil pivoted to said first airfoil and spaced therefrom so as to form a slot, a third airfoil pivoted to said rst airfoil above and forward of said second airfoil in slot closing relation, a linkage mechanism carried by said rst airfoil and connected to said second and third airfoils for imparting simultaneous rotation thereto about their respective pivots in at least two directions from a neutral position each of said connections being independent of the other, iirst pilot operated means connected to said linkage mechanism for imparting movement thereto, and second pilot operated means for displacing said second airfoil from its iirst neutral position to different neutral positions said linkage mechanism being constructed and connected to said second airfoil to impart said rotation to said second airfoil in at least two directions from each of said diierent neutral positions.

- 11i. In -a lateral control device for aircraft, a

i2" first airfoil, a second airfoil pivoted to said -rst air-foil and spaced therefrom so as to form a slot, a third airfoil pivoted to said rst airfoil and adapted to overlie said slot, a linkage mechanism carried by said rst airfoil and connected and'with respect thereto, a rst link meansv connecting said crank means to said second airfoil, a second link means connecting said crank means to said third airfoil independently of the connection of said rst link means to said second airfoil, rst pilot operated means pivoted to said carrier member for rotating said member on itspivot to change the position of said second airfoil pivot relative to said first airioil, and second pilot operated means pivoted to said crank means for moving said crank means relative to said carrier member to rotate both said second and third airfoils about their respective pivots and vary the size of the slot between said rst and second airfoils.

12. In a lateral control device for aircraft, the combination of a main supporting airfoil; a control flap aft the trailing edge of said main supporting airfoil, said iiap being supported for pivotal movement about an axis spanwise of the airfoil; a control slot lip overlying the slot between the airfoil and ap, the slot lip bein-g supported for pivotalV movement about an axis parallel to said axis and in'slot-closing relation with the airfoil; a rst means for moving the pivotal support of the ap over an upper fore and lower aft range between a forward slot-closing position and an aft-displaced maximum slot-opening position with relation to the airfoil and for varying the inclination of the ap to the horizontal, the outwardly exposed surfaces of the slot lip and flap fairing with the surfaces of the airfoil in said forward slot-closing position and the iiap being inclined increasingly downwardly in substantially direct correlation with the extent oi said. aft displacement from the airfoil; and a second means for co-ordinately and codirectionally moving the nap and slot lip about their axesv over a limited angular travel range above and below a neutral position for aileron roll control, said second means being operative at any position of the flap over saidfore and aftV range to effect a substantial and effective aileron movement of the slot lip, and being operative at any position of the iiap over at least the more forward portion of said range to effect a substantial and effective'aileron movement of the flap.

13. The combination defined in claim l2 in which said slot between the slot lip and flap is substantially closed at all aileron positions of the slot lip and iiap with the flap in said slot closing position and in which said slot between the slot lipand flap progressively increases in width for corresponding aileron positions as the ilap is moved rearwardly and downwardly by said rst means. A

14. The combination dened in claim 12A in which said slot betweenA the slot lip and flap is substantially closedat lallaileron positions of the slot up and flap with the flap irl said 'slot closing position and in which said slot between,

Width for corresponding aileron positions as the 13 flap is moved rearwardly and downwardly by said first means at least during a substantial first portion of said rearward and downward movement.

l5. The combination defined in claim 12 in which said slot between the slot lip and flap is f slot lip and flap for any given fore and aft iiap position increases in width from a minimum at the extreme down aileron position to a maximum at the extreme up aileron position.

16. The combination defined in claim 12 in which the slot between said slot lip and flap is substantially closed at all aileron positions ci said slot lip and flap with said flap in said slot closing position and the slot between said slot lip and flap progressively increases in width to a maximum for corresponding aileron positions as the flap is moved rearwardly and downwardly by said first means and the slot lip is disposed wit its under surface directed to prevent air separation from the upper surface of said flap in the downward portion only of the range of the aileron movement given said iiap and slot lip by said second means.

17. The combination dened in claim 12 in which the slot between said slot lip and flapI is substantially closed at al1 aileron positions of said slot lip and flap with said flap in said slot closing position and the slot between said slot lip and flap progressively increases to a maximum for corresponding aileron positions as the flap is moved rearwardly and downwardly by said rst means, the slot between said slot lip and flap for any given fore and aft flap position increases in width from a minimum at the extreme down aileron position to a maximum at the eXtreme up aileron position and the slot lip is disposed with its under surface directed to prevent air separation from the upper surface of said ap in the downward portion only of the range of the aileron movement given said flap and slot lip by said second means. l

18. The combination dened in claim 12 in which as said flap is moved rearwardly over said fore and aft range by said first means the angular range of aileron movement of said flap by said second means has no substantial increase and the angular range of aileron movement of said slot lip by said second means substantially increases.

19. The combination defined in claim 12 in which the neutral and extreme positions of the slot lip for roll control for the more rearward portion of the fore and aft range of movement of the flap are respectively higher than the corresponding roll control positions of the slot lip in the more forward portion of said fore and aft range.

`termined by said nrst 20. In a lateral control device for aircraft, a rst airfoil, a second airfoil pivoted to said first airfoil and rearwardly displaceable therefrom so as to form a slot of varying dimensions, and means movable, in al1 positions of rearward displacement of said second airfoil, to increase the size of said slot with lift decreasing pivotal movement of said second airioil relative to said first airfoil and to decrease the size of said slot with lift increasing pivotal movement of said second airfoil relative to said first airfoil.

2l. In a lateral control device for aircraft, a first airfoil, a second airfoil pivoted to said first airfoil and spaced therefrom so as to form a slot therebetween, a third .airfoil pivoted to said first airfoil above and forward of said second airfoil pivot in slot closing relation, both said second and third airfoils cooperating when in their normal positions to form a substantial continuation of said first airfoil, first pilot operated means for moving said second airfoil aft and downward from said normal position with respect to said rst airfoil to one or several second positions wherein said slot is increased in size, and from said second positions to a third position wherein said slot is further changed in size, and second pilot operated means for simultaneously rotating both said second and third airfoils about their respective pivotal connections to said first airfoil in varying relative amounts depending upon their relative positions as depilot operated means, said third airfoil being rotatable in said third position to at least the degree of rotation possible when in said second positions.

22. In a lateral control device for aircraft, a first airfoil, a second airfoil carried by said first airfoil for pivotal movement and spaced therefrom so as to form a slot therebetween, a third airfoil pivoted to said first airfoil above and onward of said second airfoil pivot in slot closing relation, both said second .and third airioils cooperating when in their normal positions to form a substantial continuation of said first airoil, rst pilot operated means for moving said second airfoil aft and downward from said normal position with respect to said rst airfoil to one or several second positions wherein said slot is increased in size, and from said second positions to a third position wherein said slot is further changed in size, second pilot operated means for simultaneously rotating both said second and third airfoils about their respective pivotal connections to said rst airfoil, and means interconnecting said first and second pilot operated means for varying the relative rotative movements of said second and third airfoils in accordance with their varying relative lpositions, said third airfoil being rotatable in said third position to at least the degree of rotation possible when in said second positions.

FRANCIS H. CLAUSER. CARLOS C. WOOD. 

